Improved Limiting Criteria for Deflection in Multi-Story Buildings Subjected to Aerodynamic Load

AbstractFor the entry guidance problem of hypersonic gliding vehicles (HGVs), an analytical predictor–corrector guidance method based on feedback control of bank angle is proposed. First, the relative functions between the velocity, bank angle and range-to-go are deduced, and then, the analytical relation is introduced into the predictor–corrector algorithm, which is used to replace the traditional method to predict the range-to-go via numerical integration. To eliminate the phugoid trajectory oscillation, a method for adding the aerodynamic load feedback into the control loop of the bank angle is proposed. According to the quasi-equilibrium gliding condition, the function of the quasi-equilibrium glide load along with the velocity variation is derived. For each guidance period, the deviation between the real-time load and the quasi-equilibrium gliding load is revised to obtain a smooth reentry trajectory. The simulation results indicate that the guidance algorithm can adapt to the mission requirements of different downranges, and it also has the ability to guide the vehicle to carry out a large range of lateral maneuvers. The feedback control law of the bank angle effectively eliminates the phugoid trajectory oscillation and guides the vehicle to complete a smooth reentry flight. The Monte Carlo test indicated that the guidance precision and robustness are good.

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Closed loop control of aerodynamic load fluctuations on wind turbine airfoil using surface plasma actuators

IFAC-PapersOnLine ◽

10.1016/j.ifacol.2020.12.1848 ◽

2020 ◽

Vol 53 (2) ◽

pp. 12675-12681

Author(s):

Dominique Nelson-Gruel ◽

Pierrick Joseph ◽

Alexis Paulh-Manssens ◽

Annie Leroy ◽

Sandrine Aubrun ◽

...

Keyword(s):

Wind Turbine ◽

Closed Loop ◽

Plasma Actuators ◽

Aerodynamic Load ◽

Closed Loop Control ◽

Surface Plasma ◽

Loop Control ◽

Wind Turbine Airfoil

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Pre-Deformation Method for Manufactured Compressor Blade Based on Load Incremental Approach

International Journal of Turbo and Jet Engines ◽

10.1515/tjj-2017-0024 ◽

2020 ◽

Vol 37 (3) ◽

pp. 259-265

Author(s):

Kang Da ◽

Wang Yongliang ◽

Zhong Jingjun ◽

Liu Zihao

Keyword(s):

Compressor Blade ◽

Aerodynamic Load ◽

Deformation Method ◽

Transonic Compressor ◽

Incremental Approach ◽

Compressor Rotor ◽

Centrifugal Load ◽

Blade Shape ◽

Stationary Shape ◽

Deformation Procedure

AbstractThe blade deformation caused by aerodynamic and centrifugal loads during operating makes blade configurations different from their stationary shape. Based on the load incremental approach, a novel pre-deformation method for cold blade shape is provided in order to compensate blade deformation under running. Effect of nonlinear blade stiffness is considered by updating stiffness matrix in response to the variation of blade configuration when calculating deformations. The pre-deformation procedure is iterated till a converged cold blade shape is obtained. The proposed pre-deformation method is applied to a transonic compressor rotor. Effect of load conditions on blade pre-deformation is also analyzed. The results show that the pre-deformation method is easy to implement with fast convergence speed. Neither the aerodynamic load nor centrifugal load can be neglected in blade pre-deformation.

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Investigation on flow field structure and aerodynamic load in vacuum tube transportation system

Journal of Wind Engineering and Industrial Aerodynamics ◽

10.1016/j.jweia.2021.104681 ◽

2021 ◽

Vol 215 ◽

pp. 104681

Author(s):

Sha Zhong ◽

Bosen Qian ◽

Mingzhi Yang ◽

Fan Wu ◽

Tiantian Wang ◽

...

Keyword(s):

Flow Field ◽

Transportation System ◽

Field Structure ◽

Aerodynamic Load ◽

Vacuum Tube

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Design of an Intermediate Turbine Duct Downstream of a High Pressure Turbine

Volume 2A: Turbomachinery ◽

10.1115/gt2016-56476 ◽

2016 ◽

Author(s):

Chaoshan Hou ◽

Hu Wu

Keyword(s):

High Pressure ◽

Three Dimensional ◽

Low Pressure ◽

Aerodynamic Load ◽

Duct Flow ◽

Original Design ◽

High Pressure Turbine ◽

Intermediate Turbine Duct ◽

Low Pressure Turbine ◽

Inlet Conditions

The flow leaving the high pressure turbine should be guided to the low pressure turbine by an annular diffuser, which is called as the intermediate turbine duct. Flow separation, which would result in secondary flow and cause great flow loss, is easily induced by the negative pressure gradient inside the duct. And such non-uniform flow field would also affect the inlet conditions of the low pressure turbine, resulting in efficiency reduction of low pressure turbine. Highly efficient intermediate turbine duct cannot be designed without considering the effects of the rotating row of the high pressure turbine. A typical turbine model is simulated by commercial computational fluid dynamics method. This model is used to validate the accuracy and reliability of the selected numerical method by comparing the numerical results with the experimental results. An intermediate turbine duct with eight struts has been designed initially downstream of an existing high pressure turbine. On the basis of the original design, the main purpose of this paper is to reduce the net aerodynamic load on the strut surface and thus minimize the overall duct loss. Full three-dimensional inverse method is applied to the redesign of the struts. It is revealed that the duct with new struts after inverse design has an improved performance as compared with the original one.

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Cable Suspension and Balance System with Low Support Interference and Vibration for Effective Wind Tunnel Tests

International Journal of Aeronautical and Space Sciences ◽

10.1007/s42405-021-00390-y ◽

2021 ◽

Author(s):

Keum-Yong Park ◽

Yeol-Hun Sung ◽

Jae-Hung Han

Keyword(s):

Wind Tunnel ◽

Vibration Suppression ◽

Aerodynamic Load ◽

Test Model ◽

Wind Tunnel Tests ◽

Balance System ◽

Motion Responses ◽

Vibration Responses ◽

Aerodynamic Interference ◽

Support Interference

AbstractA cable-driven model support concept is suggested and implemented in this paper. In this case, it is a cable suspension and balance system (CSBS), which has the advantages of low support interference and reduced vibration responses for effective wind tunnel tests. This system is designed for both model motion control and aerodynamic load measurements. In the CSBS, the required position or the attitude of the test model is realized by eight motors, which adjust the length, velocity, and acceleration of the corresponding cables. Aerodynamic load measurements are accomplished by a cable balance consisting of eight load cells connected to the assigned cables. The motion responses and load measurement outputs were in good agreement with the reference data. The effectiveness of the CSBS against aerodynamic interference and vibration is experimentally demonstrated through comparative tests with a rear sting and a crescent sting support (CSS). The advantages of the CSBS are examined through several wind tunnel tests of a NACA0015 airfoil model. The cable support of the CSBS clearly showed less aerodynamic interference than the rear sting with a CSS, judging from the drag coefficient profile. Additionally, the CSBS showed excellent vibration suppression characteristics at all angles of attack.

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Sail Aero-Structures: Studying Primary Load Paths and Distortion

10.5957/csys-2005-015 ◽

2005 ◽

Author(s):

Robert Ranzenbach ◽

Zhenlong Xu

Keyword(s):

Aerodynamic Load ◽

Element Analysis ◽

Strain Behavior ◽

Construction Methods ◽

Load Paths ◽

Calculation Results ◽

Computational Fluid Dynamics Cfd ◽

Aerodynamic Field ◽

The Impact ◽

Primary Load

A method is described to conduct an integrated Fluid-Structure Interaction (FSI) simulation of sails that is based upon knowledge of the sail’s design shape geometry and membrane material properties. A Finite Element Analysis (FEA) of the sail structure and a Computational Fluid Dynamics (CFD) model of the aerodynamic field are combined and iteratively solved to compute the actual flying shape of the sail under aerodynamic load, the stress strain behavior of the sail membrane, the integrated aerodynamic forces produced by the sail such as driving force and heel moment, and the resulting loads on sheets, halyards, etc. An important contribution of this particular method is the incorporation of wrinkling phenomena into the FEA portion of the calculation. Results from a study of working sails for a 30’ MORC racing yacht designed by Nelson-Marek (NM) in the 1990’s are presented and discussed with particular emphasis on the variability of primary load paths with changing trim and sailing conditions as well as the impact of sail deformation in the direction of relatively small stresses that is often poorly addressed in many proprietary sail construction methods.

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Dynamic Stall Flow Structure and Forces on Symmetrical Airfoils at High Angles of Attack and Rotation Rates

Journal of Fluids Engineering ◽

10.1115/1.4041523 ◽

2018 ◽

Vol 141 (5) ◽

Cited By ~ 2

Author(s):

R. R. Leknys ◽

M. Arjomandi ◽

R. M. Kelso ◽

C. H. Birzer

Keyword(s):

Flow Structure ◽

Boundary Layer Separation ◽

Vortex Structures ◽

Dynamic Stall ◽

Aerodynamic Load ◽

Laminar Separation ◽

Rotation Rates ◽

Constant Pitch ◽

Separation Bubbles ◽

Laminar Separation Bubbles

This article describes a direct comparison between two symmetrical airfoils undergoing dynamic stall at high, unsteady reduced frequencies under otherwise identical conditions. Particle image velocimetry (PIV) was performed to distinguish the differences in flow structure between a NACA 0021 and a NACA 0012 airfoil undergoing dynamic stall. In addition, surface pressure measurements were performed to evaluate aerodynamic load and investigate the effect of laminar separation bubbles and vortex structures on the pressure fields surrounding the airfoils. Airfoil geometry is shown to have a significant effect on flow structure development and boundary layer separation, with separation occurring earlier for thinner airfoil sections undergoing constant pitch-rate motion. Inertial forces were identified to have a considerable impact on the overall force generation with increasing rotation rate. Force oscillation was observed to correlate with multiple vortex structures shedding at the trailing-edge during high rotation rates. The presence of laminar separation bubbles on the upper and lower surfaces was shown to dramatically influence the steady-state lift of both airfoils. Poststall characteristics are shown to be independent of airfoil geometry such that periodic vortex shedding was observed for all cases. However, the onset of deep stall is delayed with increased nondimensional pitch rate due to the delay in initial dynamic-stall vortex.

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First-Order Frequency Effects in Supersonic Panel Flutter of Finite Cylindrical Shells

Journal of Applied Mechanics ◽

10.1115/1.3423007 ◽

1973 ◽

Vol 40 (2) ◽

pp. 464-470

Author(s):

M. Holt ◽

T. M. Lee

Keyword(s):

Mach Number ◽

Elastic Shell ◽

Order Effect ◽

Aerodynamic Load ◽

Panel Flutter ◽

Thin Cylindrical Shell ◽

First Order ◽

Flutter Boundary ◽

Shell Equation ◽

Set Up

An improved calculation of the supersonic panel flutter characteristics of a thin cylindrical shell of finite length is presented. The aerodynamic load is determined with account taken of first-order terms in vibration frequency, and when this is introduced into the elastic shell equation an integro differential equation results. An equivalent eigenvalue problem is set up by applying Galerkin’s method to this equation. The flutter boundary, for given Mach number and circumferential mode n, corresponds to the shell thickness ratio at which the real part of any one of the eigenvalues first becomes non-negative. It is found that the most severe flutter condition, for given Mach number, occurs for a circumferential mode n = 7. The present calculations exclude second-order frequency terms in the elastic part of the flutter equation, even though they may have a first-order effect. A subsequent calculation referred to here shows that these terms indeed have no significant influence on the first-order analysis.

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Instability of Heated Panels in Supersonic Air Flow

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.33-37.1101 ◽

2008 ◽

Vol 33-37 ◽

pp. 1101-1108

Author(s):

Zhi Chun Yang ◽

Wei Xia

Keyword(s):

Stability Analysis ◽

Stability Boundary ◽

Boundary Curve ◽

Static Stability ◽

Static Deformation ◽

Limit Cycle Oscillation ◽

Aerodynamic Load ◽

Aeroelastic System ◽

Aerodynamic Pressure ◽

The Stability

An investigation on the stability of heated panels in supersonic airflow is performed. The nonlinear aeroelastic model for a two-dimensional panel is established using Galerkin method and the thermal effect on the panel stiffness is also considered. The quasi-steady piston theory is employed to calculate the aerodynamic load on the panel. The static and dynamic stabilities for flat panels are studied using Lyapunov indirect method and the stability boundary curve is obtained. The static deformation of a post-buckled panel is then calculated and the local stability of the post-buckling equilibrium is analyzed. The limit cycle oscillation of the post-buckled panel is simulated in time domain. The results show that a two-mode model is suitable for panel static stability analysis and static deformation calculation; but more than four modes are required for dynamic stability analysis. The effects of temperature elevation and dimensionless parameters related to panel length/thickness ratio, material density and Mach number on the stability of heated panel are studied. It is found that panel flutter may occur at relatively low aerodynamic pressure when several stable equilibria exist for the aeroelastic system of heated panel.

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